The Bell 212 is a medium utility helicopter initially produced by Bell Helicopter in Fort Worth, Texas, United States before it was relocated to Mirabel, Quebec, Canada. The Bell 212 is powered by a single Pratt and Whitney turboshaft engine and can fly at speeds of 100 knots.

Bell Helicopter
United States
1968 to: 1998
US$4.9 million (2019)
1x Pratt & Whitney Canada PT6T-3
1,800 horsepower
Max Cruise Speed:
120 knots
222 Km/h
Approach Speed (Vref):
Travel range:
250 Nautical Miles
463 Kilometers
Fuel Economy:
Service Ceiling:
17,400 feet
Rate of Climb:
1745 feet / minute
8.86metre / second
Take Off Distance:
Landing Distance:
Max Take Off Weight:
5,080 Kg
11,199 lbs
Max Landing Weight:
Max Payload:
2,130 Kg
4,696 lbs
Fuel Tank Capacity:
296 gallon
1,120 litre
Baggage Volume:
Seats - Economy / General:
15 seats
Seats - Business Class:
Seats - First Class:
Cabin Height:
1.2 metre - 3.94 feet
Cabin Width:
2.4 metre - 7.87 feet
Cabin Length:
2.7 metre - 8.86 feet
Exterior Length:
17.4 metre - 57.09 feet
Tail height:
3.8 metre - 12.47 feet
Fuselage Diameter:
2.6 metre - 8.53 feet
Wing Span / Rotor Diameter:
14.6 metre - 47.90 feet
Wing Tips:
No Winglets

The Bell 212 was a derivative of the Bell 205 and was initially designed for the Canadian Air Forces with the designation CUH-1N before it was changed to CH-135. In May 1971, the delivery of fifty helicopters to the Canadian Air Force began.

Concurrently, two hundred and ninety-four Bell 212s designated as UH-1N were ordered by the United States Armed Forces. In the same year, the helicopter started to explore its options in commercial service. One of the uses of the Bell 212 during the early years in civil aviation was by CHC Helicopter in Norway as an offshore helicopter.

Nowadays, the Bell 212 are used in logging operations, air-sea rescue, and replenish in the far northern Arctic region.

The main rotor of the Bell 212 is powered by a single PT6T-3 Twin-Pac engine of Pratt and Whitney. It consists of two PT6A power turbines that drive a common output reduction gearbox. The engine can produce a maximum power of up to 1,800 shaft horsepower.

If one power section suffered failure, the surviving power section can still produce a 900 shaft horsepower for thirty minutes or 765 shaft horsepower continually, allowing the helicopter to sustain performance on cruise at full weight. The main rotor diameter is 14.63 meters and the main rotor area is 168.11 square meters.

Early helicopters designed with an Instrument Flight Rules (IFR) were necessary to have a large and visible fin mounted to the roof of the helicopter, on top and further at the back of the cockpit. The Bell 212 has an external length of 17.4 meters, a height of 3.8 meters, and a width of 2.6 meters. The cabin length is 2.7 meters, the cabin height is 1.2 meters, and the cabin width is 2.4 meters. It can accommodate up to 14 passengers.

The Bell 212 has a cruise speed of 100 knots and a travel range of 237 nautical miles. It can fly up to 17,400 feet and can climb at a rate of 1,745 feet per minute.

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